Airworthiness directives › 2019-10-07
AD 2019-10-07 Airworthiness Directives; Pilatus Aircraft Ltd. Airplanes
Makes named: pilatus. Models named: PC-6, PC-6/350, PC-6/350-H1, PC-6/350-H2, PC-6/A, PC-6/A-H1, PC-6/A-H2, PC-6/B-H2, PC-6/B1-H2, PC-6/B2-H2. Read the applicability below — it usually turns on serial or part numbers too.
Applicability*9
This AD applies to Pilatus Aircraft Ltd. Models PC-6, PC-6/350, PC-6/350-H1, PC-6/350-H2, PC-6/A, PC-6/A-H1, PC-6/A-H2, PC-6/B-H2, PC-6/B1-H2, PC-6/B2-H2, PC-6/B2-H4, PC-6/C-H2, PC-6/C1-H2, PC-6-H1, PC-6-H2 airplanes, all serial numbers, certificated in any category. Note 1 to paragraph (c): These airplanes may also be identified as Fairchild Republic Company airplanes, Fairchild Industries airplanes, Fairchild Heli Porter airplanes, or Fairchild-Hiller Corporation airplanes.
Compliance
Unless already done, do the following actions in paragraphs (f)(1) and (2). (1) Within the next 100 hours time-in-service after July 10, 2019 (the effective date of this AD) or within the next 12 months after July 10, 2019 (the effective date of this AD), whichever occurs first: (i) Inspect the left-hand and the right-hand horizontal stabilizer hinge bracket assemblies for cracks, loose screws and rivets, sheared rivets, missing rivets, and looseness of the electrical bonding strap, and inspect the top and bottom screws at each hinge bracket. Repair or replace any parts with discrepancies before further flight. You must do the actions required by this paragraph by following sections C through H of the Accomplishment Instructions-Part 1-On Aircraft in Pilatus Aircraft Ltd. PC-6 Service Bulletin No. 55-004, dated July 2, 2018. (ii) Install four “DO NOT PUSH” placards, part number 110.71.06.847 or 110.71.06.848, on the horizontal stabilizer by following section G of the Accomplishment Instructions—Aircraft in Pilatus Aircraft Ltd. PC-6 Service Bulletin No. 55-002, Revision. No. 1, dated February 18, 2016. (2) After July 10, 2019 (the effective date of this AD), do not install a horizontal stabilizer on any airplane unless it has been inspected as specified in paragraph (f)(1)(i) of this AD and found to be free of discrepancies or all discrepancies have been repaired or replaced.
Required actions
The following provisions also apply to this AD: (1) Alternative Methods of Compliance (AMOCs): The Manager, Small Airplane Standards Branch, FAA, has the authority to approve AMOCs for this AD, if requested using the procedures found in 14 CFR 39.19. Send information to ATTN: Doug Rudolph, Aerospace Engineer, FAA, Small Airplane Standards Branch, 901 Locust, Room 301, Kansas City, Missouri 64106; telephone: (816) 329-4059; fax: (816) 329-4090; email: doug.rudolph@faa.gov. Before using any approved AMOC on any airplane to which the AMOC applies, notify your appropriate principal inspector (PI) in the FAA Flight Standards District Office (FSDO), or lacking a PI, your local FSDO. (2) Contacting the Manufacturer: For any requirement in this AD to obtain corrective actions from a manufacturer, the action must instead be accomplished using a method approved by the Manager, Small Airplane Standards Branch, FAA, or the European Aviation Safety Agency (EASA).
Unsafe condition
This AD was prompted by mandatory continuing airworthiness information (MCAI) originated by an aviation authority of another country to identify and correct an unsafe condition on an aviation product. The MCAI describes the unsafe condition as sheared or missing rivets on the horizontal stabilizer hinge bracket assemblies. The FAA is issuing this AD to prevent failure of the primary horizontal stabilizer load path, which could lead to separation of the horizontal stabilizer and result in loss of control of the airplane.
Affected ADs
None.
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